Accession Number : AD0757217

Title :   The Low Hub-Tip Ratio Supersonic Axial-Flow Compressor. Volume II.

Descriptive Note : Final rept. 1 Jul 71-30 Jun 72,

Corporate Author : VON KARMAN INST FOR FLUID DYNAMICS RHODE-SAINT-GENESE (BELGIUM) TURBOMACHINERY LAB

Personal Author(s) : Breugelmans,Frans A. E.

Report Date : NOV 1972

Pagination or Media Count : 72

Abstract : The report describes the test results of a supersonic axial-flow compressor stage with a tip Mach number of 2.0. This volume discusses a method to eliminate the inlet problem. (Author)

Descriptors :   (*AXIAL FLOW COMPRESSORS, STALLING), INLET GUIDE VANES, COMPRESSOR ROTORS, COMPRESSOR STATORS, SUPERSONIC FLOW, FLOW FIELDS, CASCADE STRUCTURES, PRESSURE, PERFORMANCE(ENGINEERING)

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE